This paper examines in detail some modifications to main rotor aerodynamic modeling that will affect the off-axis response of a helicopter. Three different approaches are examined: a version of momentum theory extended to include wake distortion, a first-order aerodynamic lag model, and an aerodynamic phase correction. it is shown that all three approaches result in similar changes to the off-axis response when applied to a simplified linear model of the coupled pitch-roll dynamics in hover. Numerical values for the inflow parameters are determined using system identification and are compared to theoretical predictions and previously identified values. Comparisons are also made between a nonlinear simulation model incorporating the extended momentum theory and flight test data for a UH-60 in hover, demonstrating considerable improvement in the off-axis response prediction.


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    Titel :

    The effect of inflow models on the predicted response of helicopters


    Beteiligte:
    Arnold, U.T.P. (Autor:in) / Keller, J.D. (Autor:in) / Curtiss, H.C. jun. (Autor:in) / Reichert, G. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1998


    Format / Umfang :

    12 Seiten, 15 Bilder, 2 Tabellen, 14 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





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